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Joukovsky f=0% t=9% (joukowsk0009-jf) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: Joukovsky f=0% t=9% (joukowsk0009-jf)
Reynolds number: 200,000
Max Cl/Cd: 44.23 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-joukowsk0009-jf-200000.txt
Download as CSV file: xf-joukowsk0009-jf-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Joukovsky f=0% t=9%                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.8969   0.06462   0.06071  -0.0104   1.0000   0.0346
 -10.500  -0.9182   0.05940   0.05537  -0.0125   1.0000   0.0343
 -10.250  -0.9370   0.05491   0.05068  -0.0127   1.0000   0.0340
 -10.000  -0.9486   0.05011   0.04556  -0.0128   1.0000   0.0339
  -9.750  -0.9527   0.04562   0.04067  -0.0126   1.0000   0.0340
  -9.500  -0.9483   0.04241   0.03696  -0.0120   1.0000   0.0347
  -9.250  -0.9432   0.03787   0.03193  -0.0114   1.0000   0.0354
  -9.000  -0.9308   0.03382   0.02756  -0.0110   1.0000   0.0362
  -8.750  -0.9126   0.03127   0.02479  -0.0105   1.0000   0.0372
  -8.500  -0.8922   0.02923   0.02253  -0.0100   1.0000   0.0385
  -8.250  -0.8706   0.02734   0.02040  -0.0095   1.0000   0.0401
  -8.000  -0.8477   0.02586   0.01866  -0.0090   1.0000   0.0424
  -7.750  -0.8247   0.02405   0.01655  -0.0084   1.0000   0.0447
  -7.500  -0.8016   0.02220   0.01469  -0.0080   1.0000   0.0474
  -7.250  -0.7770   0.02109   0.01348  -0.0076   1.0000   0.0507
  -7.000  -0.7513   0.02034   0.01253  -0.0071   1.0000   0.0544
  -6.750  -0.7283   0.01861   0.01088  -0.0066   1.0000   0.0592
  -6.500  -0.7028   0.01778   0.00995  -0.0062   1.0000   0.0647
  -6.250  -0.6787   0.01664   0.00885  -0.0058   1.0000   0.0720
  -6.000  -0.6536   0.01573   0.00792  -0.0053   1.0000   0.0808
  -5.750  -0.6284   0.01494   0.00714  -0.0050   1.0000   0.0932
  -5.500  -0.6035   0.01407   0.00640  -0.0047   1.0000   0.1102
  -5.250  -0.5781   0.01332   0.00574  -0.0044   1.0000   0.1352
  -5.000  -0.5528   0.01256   0.00518  -0.0042   1.0000   0.1695
  -4.750  -0.5272   0.01192   0.00474  -0.0040   1.0000   0.2122
  -4.500  -0.5013   0.01137   0.00439  -0.0039   1.0000   0.2581
  -4.250  -0.4753   0.01091   0.00410  -0.0037   1.0000   0.3036
  -4.000  -0.4491   0.01052   0.00387  -0.0034   1.0000   0.3472
  -3.750  -0.4229   0.01018   0.00367  -0.0031   1.0000   0.3885
  -3.500  -0.3966   0.00989   0.00350  -0.0028   1.0000   0.4286
  -3.250  -0.3705   0.00962   0.00337  -0.0024   1.0000   0.4659
  -3.000  -0.3444   0.00939   0.00325  -0.0020   1.0000   0.5021
  -2.750  -0.3187   0.00917   0.00316  -0.0015   1.0000   0.5362
  -2.500  -0.2933   0.00897   0.00309  -0.0009   1.0000   0.5690
  -2.250  -0.2685   0.00879   0.00304  -0.0002   1.0000   0.6006
  -2.000  -0.2447   0.00864   0.00301   0.0007   1.0000   0.6313
  -1.750  -0.2223   0.00851   0.00301   0.0018   1.0000   0.6609
  -1.500  -0.2016   0.00841   0.00305   0.0031   1.0000   0.6900
  -1.250  -0.1621   0.00836   0.00312   0.0007   0.9871   0.7225
  -1.000  -0.1173   0.00831   0.00319  -0.0024   0.9696   0.7543
  -0.750  -0.0782   0.00826   0.00324  -0.0041   0.9469   0.7836
  -0.500  -0.0459   0.00823   0.00328  -0.0041   0.9211   0.8113
  -0.250  -0.0211   0.00822   0.00331  -0.0025   0.8933   0.8386
   0.000   0.0000   0.00822   0.00331   0.0000   0.8658   0.8659
   0.250   0.0211   0.00822   0.00331   0.0025   0.8386   0.8933
   0.500   0.0459   0.00823   0.00328   0.0041   0.8114   0.9211
   0.750   0.0782   0.00826   0.00324   0.0041   0.7836   0.9469
   1.000   0.1173   0.00831   0.00319   0.0023   0.7543   0.9696
   1.250   0.1621   0.00836   0.00312  -0.0007   0.7225   0.9871
   1.500   0.2017   0.00841   0.00305  -0.0031   0.6900   1.0000
   1.750   0.2224   0.00851   0.00301  -0.0018   0.6609   1.0000
   2.000   0.2448   0.00864   0.00301  -0.0007   0.6312   1.0000
   2.250   0.2686   0.00879   0.00304   0.0001   0.6007   1.0000
   2.500   0.2934   0.00897   0.00309   0.0008   0.5690   1.0000
   2.750   0.3188   0.00917   0.00316   0.0014   0.5361   1.0000
   3.000   0.3445   0.00939   0.00325   0.0019   0.5021   1.0000
   3.250   0.3706   0.00962   0.00337   0.0024   0.4659   1.0000
   3.500   0.3967   0.00989   0.00350   0.0028   0.4286   1.0000
   3.750   0.4229   0.01018   0.00367   0.0031   0.3885   1.0000
   4.000   0.4492   0.01052   0.00387   0.0034   0.3472   1.0000
   4.250   0.4753   0.01091   0.00410   0.0036   0.3037   1.0000
   4.500   0.5014   0.01137   0.00439   0.0039   0.2582   1.0000
   4.750   0.5272   0.01192   0.00474   0.0040   0.2121   1.0000
   5.000   0.5528   0.01256   0.00518   0.0042   0.1695   1.0000
   5.250   0.5781   0.01332   0.00574   0.0044   0.1352   1.0000
   5.500   0.6035   0.01407   0.00640   0.0047   0.1102   1.0000
   5.750   0.6284   0.01494   0.00715   0.0050   0.0932   1.0000
   6.000   0.6537   0.01573   0.00792   0.0053   0.0809   1.0000
   6.250   0.6787   0.01663   0.00885   0.0058   0.0719   1.0000
   6.500   0.7027   0.01777   0.00995   0.0062   0.0647   1.0000
   6.750   0.7281   0.01861   0.01088   0.0067   0.0592   1.0000
   7.000   0.7511   0.02034   0.01253   0.0072   0.0544   1.0000
   7.250   0.7767   0.02109   0.01348   0.0076   0.0507   1.0000
   7.500   0.8013   0.02220   0.01469   0.0081   0.0475   1.0000
   7.750   0.8243   0.02405   0.01655   0.0085   0.0447   1.0000
   8.000   0.8471   0.02584   0.01863   0.0091   0.0424   1.0000
   8.250   0.8699   0.02731   0.02037   0.0096   0.0401   1.0000
   8.500   0.8914   0.02920   0.02249   0.0102   0.0385   1.0000
   8.750   0.9116   0.03125   0.02478   0.0107   0.0372   1.0000
   9.000   0.9297   0.03376   0.02750   0.0112   0.0362   1.0000
   9.250   0.9424   0.03772   0.03177   0.0117   0.0354   1.0000
   9.500   0.9471   0.04247   0.03701   0.0122   0.0348   1.0000
   9.750   0.9516   0.04565   0.04067   0.0128   0.0342   1.0000
  10.000   0.9481   0.04992   0.04536   0.0131   0.0339   1.0000
  10.250   0.9365   0.05476   0.05052   0.0130   0.0341   1.0000
  10.500   0.9180   0.05928   0.05524   0.0128   0.0343   1.0000
  10.750   0.8976   0.06437   0.06045   0.0108   0.0346   1.0000
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